Abstract
In order to simulate the influence of intake distortion on the performance and stability of multi-stage axial compressor accurately, an improved split actuator disk (SAD) model is developed based on actuator disk models. By comparing the simulation with the original model, it is verified that the split actuator disk model is more accurate. Further, the influence of the intake distortion condition on performance of multi-stage axial compressor is simulated using split actuator disk model. This paper shows that the split actuator disk can eliminate the error caused by the assumption of the original model effectively, and the simulation results are closer to the full three-dimensional simulation. Using the split actuator disk model can analyze the performance of the multi-stage compressor under the condition of total pressure distortion, and provide a feasible and accurate method for the joint simulation of the inlet-compressor system.
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References
屠宝锋, 胡骏. 轴流压气机气动稳定性的三维计算模型研究 (2008) 年航空宇航科学与技术全国博士生学术论坛
Joo WG, Hynes TP (1997) The simulation of turbomachinery blade rows in asymmetric flow using actuator disks. Trans ASME J Turbomach 119(4):723–732
Strazisar AJ, Powell JA (1989) Laser anemometer measurements in a transonic axial flow compressor rotor. Nasa Sti/recon Technical Report N, 90(2): 430–437
Fottner L (1990) Test cases for computation of internal flows in aero engine components, AGARD-AR-275
Arnone A (1994) Viscous analysis of three-dimensional rotor flow using a multigrid method. J Turbomach 116(3): V001T03A008
Steinke RJ (1986) Design of 9.271-pressure-ratio 5-stage core compressor and overall performance for first 3 stages
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Zhang, B., Wang, Q., Hu, H., Zhang, Y. (2019). The Simulation of Compressor Performance of Inlet Distortion Using Split Actuator Disk Model. In: Zhang, X. (eds) The Proceedings of the 2018 Asia-Pacific International Symposium on Aerospace Technology (APISAT 2018). APISAT 2018. Lecture Notes in Electrical Engineering, vol 459. Springer, Singapore. https://doi.org/10.1007/978-981-13-3305-7_23
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DOI: https://doi.org/10.1007/978-981-13-3305-7_23
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